斜切喷管固体火箭发动机推力特性仿真与试验  

Simulation and Experiment of Thrust Performance for Solid Rocket Motor with Angle-cut Nozzle

作　　者：邢志浩[1] 房雷[1] 王君祺[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《航空兵器》2009年第2期50-52,共3页Aero Weaponry

摘　　要：为了降低倾斜架式发射地空导弹的发射仰角,满足对超低空来袭目标的攻击需求,提出了斜切喷管预制发动机推力偏心方案,进行了流场仿真和发动机点火试验,数值模拟与试验结果吻合良好。进一步分析表明,斜切喷管方案在地空导弹上的应用是可行的。In order to decrease the launching elevation angle of tiltable firing ramp for a certain surface-to-air missile, and to meet the demands of attacking the hedge-hopping targets, the angle-cut nozzle scheme for presetting thrust misalignment of the missile engine is proposed. Flow field simulations and ignition tests are then carried out, and the experiment results are in good agreement with the numerical simulations. Further analysis shows that the proposed angle-cut nozzle scheme is feasible to the surface-to-air missile.

关 键 词：斜切喷管 固体火箭发动机 推力偏心 

分 类 号：TJ760.622[兵器科学与技术—武器系统与运用工程]